Abstract
An automatic feedback system, based on continuous monitoring of control loads, is used to find the control settings that are required to obtain a given flight condition of a helicopter rotor. Optimum values of gains and time constants are determined, the controller behavior is studied, and the limitations of the controller are examined for flap-pitch dynamics including a simple stall model. It is found that the present method shows good convergence, and it is superior to other trim techniques for systems with moderate damping or with many degrees of freedom.
| Original language | English |
|---|---|
| Pages (from-to) | 463-470 |
| Number of pages | 8 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Issue number | Pt 2, and |
| State | Published - 1981 |
| Event | AIAA Dyn Spec Conf - Atlanta, Ga Duration: Apr 6 1981 → Apr 10 1981 |